Accession Number:

ADA009168

Title:

Turbine Vane Ceramic Endwall Program.

Descriptive Note:

Final rept. 1 May 73-31 Jul 74,

Corporate Author:

PRATT AND WHITNEY AIRCRAFT EAST HARTFORD CONN

Personal Author(s):

Report Date:

1974-08-01

Pagination or Media Count:

46.0

Abstract:

The feasibility of using ceramic material for turbine vane platforms has been demonstrated. The high temperature capability of this material permits operation with reduced coolant flow, providing a turbine efficiency improvement which can be translated into improved engine performance. In the demonstration, platforms were fabricated from hot-pressed silicon nitride and tested at elevated temperature in a cascade of transpiration-cooled turbine vanes representative of advanced engine concepts. The platforms successfully completed ten hours of steady-state endurance testing with surface temperature in excess of 2000F with no damage. Subsequent thermal cyclic testing resulted in cracking near the trailing edge on two of the platforms, while the third remained intact. Analysis of the results indicates that relatively minor design modifications should solve this problem.

Subject Categories:

  • Ceramics, Refractories and Glass
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE